Methods for inspecting components

ABSTRACT

A method for inspecting a component. The method includes coupling the component to a fixture such that the component is fixedly secured in position during machining of the component, and inspecting the component using an inspection tool while the component is coupled to the fixture.

BACKGROUND OF THE INVENTION

[0001] This invention relates generally to inspection techniques, andmore specifically to methods and apparatus for inspecting components.

[0002] Accurately measuring a surface of a component may be asignificant factor in determining a manufacturing time of the component,as well in determining subsequent maintenance and repair costs andactivities. Specifically, when the component is a gas turbine engineshroud, accurately measuring the contour of the shroud may be one of themost significant factors affecting an overall cost of fabrication of thegas turbine engine, as well as subsequent modifications, repairs, andinspections of the blade airfoils. For example, at least some known gasturbine engine shroud segments are small and include a snubber sectionand a racetrack section. For performance reasons, both the snubbersection and the racetrack section require an accurately machinedthickness. However, accurately measuring the thickness of the snubberand racetrack sections may be difficult because of the relative smallsize of the shroud segment.

[0003] At least some known inspection processes use coordinate measuringmachines (CMMs) or other gages to obtain dimensional information for ashroud segment. Within at least some CMMs and gages, the thickness of asection of a shroud segment is determined by measuring a drop from asurface of the shroud segment to a surface whose location is known, suchas a fixture used with the CMM or other gage. However, determining thethickness of a section of a shroud segment by measuring the drop to aknown surface does not directly measure the thickness of the shroudsegment, and therefore may be inaccurate. Furthermore, at least someknown shroud segments must be removed from the machining apparatus priorto being inspected by a CMM or other gage. Removing the shroud segmentfrom a machining apparatus increases the number of fabricationoperations and the number of apparatuses used for manufacturing, thusincreasing manufacturing time and cost. In addition, if the shroudsegment fails the inspection, the segment may then need to bereinstalled in the machining apparatus for further machining. However,because of the size and contour of the shroud segment, it may bedifficult to reinstall the shroud segment within the machining apparatusin the same relative position with respect to the original machining,thereby increasing error and manufacturing time.

BRIEF DESCRIPTION OF THE INVENTION

[0004] In one aspect, a method is provided for inspecting a component.The method includes coupling the component to a fixture such that thecomponent is fixedly secured in position during machining of thecomponent, and inspecting the component using an inspection tool whilethe component is coupled to the fixture.

[0005] In another aspect, an inspection tool is provided. The toolincludes a first probe having a probe body, a first probe tip coupled tothe probe body, and a second probe tip coupled to the probe body. Thefirst probe is configured to inspect a component using the first andsecond probe tips.

[0006] In yet another aspect, an inspection apparatus is provided forinspecting a component. The inspection apparatus includes a machiningapparatus configured to machine the component, a fixture coupled to themachining apparatus and configured to couple to the component such thatthe component is fixedly secured in position during machining of thecomponent, and an inspection tool coupled to at least one of the fixtureand the machining apparatus. The inspection tool is configured toinspect the component while the component is coupled to the fixture.

BRIEF DESCRIPTION OF THE DRAWINGS

[0007]FIG. 1 is a schematic illustration of an exemplary gas turbineengine;

[0008]FIG. 2 is a perspective view of an exemplary gas turbine engineshroud segment included in the gas turbine engine shown in FIG. 1;

[0009]FIG. 3 is a cross-sectional view of the gas turbine engine shroudsegment shown in FIG. 2 and taken along line 3-3 of FIG. 2;

[0010]FIG. 4 is a perspective view of an inspection tool assembly forinspecting a component, such as the gas turbine engine shroud segmentshown in FIGS. 2 and 3;

[0011]FIG. 5 is a perspective view of the inspection tool assembly shownin FIG. 4 and including a fixture used for fixedly securing a component,such as the gas turbine engine shroud segment shown in FIGS. 2 and 3;

[0012]FIG. 6 is a perspective view of the fixture shown in FIG. 5illustrating the shroud segment shown in FIGS. 2 and 3 fixedly securedthereto; and

[0013]FIG. 7 is a perspective view of a snubber and racetrack probe forinspecting a component, such as the gas turbine engine shroud segmentshown in FIGS. 2 and 3.

DETAILED DESCRIPTION OF THE INVENTION

[0014] As used herein, the terms “inspection” and “inspecting” mayinclude any inspection process. For example, inspection processes mayinclude measurement by a machine, measurement by humans, visualinspection by a machine, and/or visual inspection by a human. The aboveexamples are intended as exemplary only, and thus are not intended tolimit in any way the definition and/or meaning of the terms “inspection”and “inspecting”. Also, as used herein the terms “manufacture” and“manufacturing” may include any manufacturing process. For example,manufacturing processes may include machining, inspecting, and/orcasting. The above examples are intended as exemplary only, and thus arenot intended to limit in any way the definition and/or meaning of theterms “manufacture” and “manufacturing”.

[0015] As used herein the term “component” may include any object towhich an inspection or manufacturing process is applied. Furthermore, asused herein the terms “machining” and “machined” may include any processused for shaping a component. For example, processes used for shaping acomponent may include turning, planing, milling, grinding, finishing,polishing, and/or cutting. In addition, and for example, shapingprocesses may include processes performed by a machine, a machine tool,and/or a human being. The above examples are intended as exemplary only,and thus are not intended to limit in any way the definition and/ormeaning of the terms “machining” and “machined”. In addition, as usedherein the term “machining apparatus” may include any device used tomachine a component. For example, any device used to machine a componentmay include a machine, a human, and/or a machine tool. The aboveexamples are intended as exemplary only, and thus are not intended tolimit in any way the definition and/or meaning of the term “machiningapparatus”.

[0016] Although the invention is described herein in association with agas turbine engine, and more specifically for use with a shroud segmentfor a gas turbine engine, it should be understood that the presentinvention may be applicable to any component and/or any inspectionprocess. Accordingly, practice of the present invention is not limitedto the inspection of shrouds or other components of gas turbine engines.

[0017]FIG. 1 is a schematic illustration of an exemplary gas turbineengine 10 including a low pressure compressor 12, a high pressurecompressor 14, and a combustor assembly 16. Engine 10 also includes ahigh pressure turbine 18 and a low pressure turbine 20. Compressor 12and low pressure turbine 20 are coupled by a first shaft 24, andcompressor 14 and high pressure turbine 18 are coupled by a second shaft26. Engine 10 includes an axis of symmetry 28 extending from an inletside 30 of engine 10 aftward to an exhaust side 32 of engine 10. Shafts24 and 26 rotate about axis of symmetry 28. In one embodiment, engine 10is a GE90 engine available from General Electric Aircraft Engines,Cincinnati, Ohio. In operation, air flows through low pressurecompressor 12 from inlet side 30 of engine 10 and compressed air issupplied from low pressure compressor 12 to high pressure compressor 14.Highly compressed air is then delivered to combustor assembly 16 whereit is mixed with fuel and ignited. The combustion gases are channeledfrom combustor 16 and used to drive turbines 18 and 20.

[0018]FIG. 2 is perspective view of a portion of high pressure turbine18 including an exemplary gas turbine engine shroud segment 40. FIG. 3is a cross-sectional view of shroud segment 40 taken along line 3-3 ofFIG. 2. Turbine 18 includes an outer casing (not shown) thatcircumferentially surrounds a stator assembly (not shown), a rotorassembly (not shown), and a turbine nozzle assembly (not shown). In oneembodiment, a plurality of shroud segments 40 are disposed radiallyinward from the outer casing and extend circumferentially around theturbine nozzle assembly such that adjacent shroud segments 40circumferentially contact to form a static ring shroud (not shown).Shroud segment 40 has an arcuate cross-sectional profile, and includes aradially outer side 42 and a radially inner side 44. Shroud segment 40also includes a radially outer surface 43 and a radially inner surface45. Surfaces 43 and 45 are connected by a first side 46, a front 47, asecond side 48, a back 49, a racetrack section 50, and a snubber section52. More specifically, radially inner side 44 and radially outer side 42extend between first side 46 and second side 48. In the exemplaryembodiment, radially inner side 44 is generally concentric with radiallyouter side 42 along a width 58 of segment 40. In addition, in theexemplary embodiment, radially inner side 44 is generally parallel withradially outer side 42 along a first shroud segment length 98 of segment40.

[0019] In the exemplary embodiment, first side 46 includes a firstpassageway 54 defined between racetrack section 50 and a first sideprojection 56 of segment 40. First passageway 54 extends along segmentwidth 58 from segment front 47 to segment back 49, and extends a depth60 inwardly from first side 46 towards segment second side 48. Firstpassageway 54 includes a radially outer wall 62, a side wall 64, and aradially inner wall 66. In the exemplary embodiment, side wall 64 issubstantially semi-cylindrical. Second side 48 includes a secondpassageway 68 defined between snubber section 52 and a second sideprojection 70. Second passageway 68 extends along width 58 of shroudsegment 40 from segment front 47 to segment back 49, and extends a depth72 inwardly from second side 48 towards first side 46. Second passageway68 includes a radially outer wall 74, a side wall 76, and a radiallyinner wall 78.

[0020] Racetrack section 50 includes a side surface 79 and a groove 80defined in radially outer side 42 and extending along segment width 58.Racetrack side surface 79 is illustrated in FIGS. 2 and 3 as a machinedsurface. Groove 80 includes a bottom 82, a first side 84, and a secondside 85. Snubber section 52 includes a projection 86 extending radiallyoutwardly from radially outer side 42 and radially outer surface 43.Projection 86 extends along segment width 58, and includes a projectionsurface 88 that extends outwardly from radially outer surface 43.Snubber section 52 further includes a side surface 89.

[0021] First passageway 54, second passageway 68, radially inner surface45, groove 80, projection surface 88, racetrack side surface 79, andsnubber side surface 89 are configured to be machined using a knownmachining apparatus. A distance 90 between the machined surfaces ofprojection surface 88 and outer wall 74 of second passageway 68 definesa thickness 90 for snubber 52. In addition, a distance 92 between themachined surfaces of groove bottom 82 and first passageway outer wall 62defines a thickness 92 for racetrack section 50. A distance 94 betweenthe machined surfaces of radially inner surface 45 and groove bottom 82defines a first shroud segment thickness 94. Also, a distance 96 betweenthe machined surfaces of radially inner surface 45 and projectionsurface 88 defines a second shroud segment thickness 96. Furthermore, adistance 98 between the machined surfaces of snubber side surface 89 andracetrack side surface 79 defines a first shroud segment length 98, anda distance (not shown) between snubber side surface 89 and racetrackside surface 79 before racetrack side surface 79 has been machineddefines a second shroud segment length (not shown).

[0022]FIG. 4 is a perspective view of an inspection tool assembly 100used for inspecting shroud segment 40. FIG. 5 is a perspective view ofinspection tool assembly 100 including a fixture 101 used for fixedlysecuring shroud segment 40. FIG. 6 is a perspective view of fixture 101illustrating shroud segment 40 fixedly secured thereto. Prior tomachining, shroud segment 40 is coupled to fixture 101 and fixture 101fixedly secures shroud segment 40 with respect to fixture 101 and in aposition to facilitate accurate machining of shroud segment 40 by amachining apparatus (not shown). Fixture 101 retains segment 40 duringmachining with respect to fixture 101 and in position to facilitateaccurate machining of shroud segment 40. In the exemplary embodiment,fixture 101 fixedly secures shroud segment 40 with respect to fixture101 using a clamp 103. However, it will be understood that fixture 101may fixedly secure shroud segment 40 with respect to fixture 101 usingany suitable means. In one embodiment (not shown), fixture 101 iscoupled to the machining apparatus, using any suitable means. In analternative embodiment (not shown), fixture 101 is not coupled to themachining apparatus but rather fixedly secures shroud segment 40 in aposition with respect to the machining apparatus and fixture 101 tofacilitate accurate machining of segment 40 using the machiningapparatus.

[0023] Inspection tool assembly 100 is used to inspect fixture 101, andto determine snubber thickness 90, racetrack thickness 92, first shroudsegment thickness 94, second shroud segment thickness 96, first shroudsegment length 98, and the second shroud segment length while shroudsegment 40 is coupled to fixture 101 in position to facilitate accuratemachining of segment 40.

[0024] In one embodiment, inspection tool assembly 100 is coupled to themachining apparatus, using any suitable means. For example, in oneembodiment inspection tool assembly 100 is coupled to the machiningapparatus using threaded bolts and threaded openings. Inspection toolassembly includes fixture 101, an inspection tool body 102, a fixtureprobe 104, a segment thickness probe 106, a snubber and racetrack probe108, and a segment length probe 110. Probes 104, 106, 108, and 110 arecoupled to body 102, using any suitable means. For example, in oneembodiment, at least one of probes 104, 106, 108, and 110 is coupled tobody 102 using threaded bolts and threaded nuts. In another embodiment,at least one of probes 104, 106, 108, and 110 is coupled to body 102using threaded bolts and threaded openings.

[0025] Fixture probe 104 is configured to inspect fixture 101 andincludes a first end 112, a second end 114, a probe body 116, a probetip 118, a fixture probe axis 120, a biasing mechanism 122, and aconnecting member 124. Connecting member 124 is coupled to inspectiontool assembly body 102 and probe body 116 is received within an opening126 that extends through a length 127 of connecting member 124. Biasingmechanism 122 is coupled to probe body 116 and probe tip 118, and biasesprobe tip 118 away from connecting member 124 along axis 120. Whenfixture 101 is in a position with respect to inspection tool assembly100 to facilitate inspection of fixture 101, biasing mechanism 122biases probe tip 118 to contact a surface (not shown) of fixture 101. Inone embodiment, biasing mechanism 122 is a spring. However, it should beunderstood that biasing mechanism 122 may be any biasing mechanismsuitable for biasing probe tip 118 to contact a surface of fixture 101.Using probe tip 118, fixture probe 104 measures a location of thesurface of fixture 101. Determining the location of the surface offixture 101 allows the thermal growth of fixture 101 and machineapparatus error to be measured throughout a manufacturing cycle, andenables offsets of the machining apparatus to be corrected.

[0026] Segment thickness probe 106 is configured to inspect first shroudsegment thickness 94 and second shroud thickness 96. Segment thicknessprobe 106 includes a probe body 128 having a first end 130 and a secondend 132, a segment thickness probe axis 135, and a connecting member136. Probe body 128 includes a probe tip 134 extending outwardly fromsecond end 132. Connecting member 136 is coupled to inspection toolassembly 100 and includes an opening 138 that extends through a length140 of connecting member 136. A portion of probe body 128 is receivedwithin opening 138 and probe body 128 is fixedly secured within opening138 using any suitable means, for example threaded bolts and threadednuts. In an alternative embodiment, probe body 128 is moveable withinopening 138 such that probe body 128 is translatable and selectivelypositionable along axis 135 within opening 138. Probe tip 134 ismoveable along axis 135 and within probe body 128. More specifically,probe tip 134 is translatable and selectively positionable along axis135 within probe body 128. In addition, probe body 128 is moveable alongaxis 135 and with respect to inspection tool assembly body 102 such thatprobe body 128 is translatable and selectively positionable along axis135. Movement of probe tip 134 and probe body 128 along axis 135 isdriven by any suitable mechanism or means, such as, but not limited to,a pneumatic system or a biasing mechanism.

[0027] When shroud segment 40 and fixture 101 are in a position withrespect to inspection tool assembly 100 to facilitate inspection of atleast one of shroud segment thickness 94 and second shroud thickness 96,probe tip 134 moves along axis 135 from a position wherein probe tip 134does not contact racetrack section groove bottom 82 or snubber sectionprojection surface 88 to a position wherein probe tip 134 contactseither groove bottom 82 or projection surface 88. Segment thicknessprobe 106 is then used to measure the location of probe tip 134 andcompares the location of probe tip 134 with the location of the surfaceof fixture 101 measured by fixture probe 104 to determine either firstshroud segment thickness 94 or second shroud segment thickness 96.

[0028] Segment length probe 110 is configured to inspect first shroudsegment length 98 and the second shroud segment length. Probe 110includes a first end 142, a second end 144, a probe body 146, a probetip 148, a segment length probe axis 150, a biasing mechanism 152, and aconnecting member 154. Connecting member 154 is coupled with inspectiontool assembly body 102 and probe body 146. Probe body 146 is receivedwithin an opening 156 that extends through a length 158 of connectingmember 154. Biasing mechanism 152 is coupled to probe body 146 and probetip 148, and biases probe tip 148 away from connecting member 154 alongaxis 150. When shroud segment 40 is in position with respect toinspection tool assembly 100 to facilitate inspection of at least one offirst shroud segment length 98 and the second shroud segment length,biasing mechanism 152 biases probe tip 148 to contact at least one ofracetrack side surface 79, either before or after machining, and snubberside surface 89. In one embodiment, biasing mechanism 152 is a spring.However, it should be understood that biasing mechanism 152 may be anybiasing mechanism suitable for biasing probe tip 148 to contact at leastone of racetrack side surface 79, either before or after machining, andsnubber side surface 89.

[0029] To determine first shroud segment length 98 after racetrack sidesurface 79 has been machined, segment length probe 110 measures thelocation of probe tip 148 when probe tip 148 contacts machined racetrackside surface 79, and compares the location of probe tip 148 with a knownlocation of snubber side surface 89. Alternatively, to determine firstshroud segment length 98, segment length probe 110 measures the locationof probe tip 148 when probe tip 148 contacts snubber side surface 89,and compares the location of probe tip 148 with a known location ofmachined racetrack side surface 79. To determine the second shroudsegment length before racetrack side surface 79 has been machined,segment length probe 110 measures the location of probe tip 148 whenprobe tip 148 contacts unmachined racetrack side surface 79, andcompares the location of probe tip 148 with a known location of snubberside surface 89. Alternatively, to determine the second shroud segmentlength, segment length probe 110 measures the location of probe tip 148when probe tip 148 contacts snubber side surface 89, and compares thelocation of probe tip 148 with a known location of unmachined racetrackside surface 79.

[0030]FIG. 7 is a perspective view of snubber and racetrack probe 108.Snubber and racetrack probe 108 is configured to inspect snubberthickness 90 and racetrack thickness 92. Snubber and racetrack probe 108includes a first probe body 160, a second probe body 162, a connectingmember 164, a shaft 166, a first probe body axis 168, and a shaft axis170. First probe body axis 168 is generally parallel to shaft axis 170and thus, first probe body 160 is generally parallel to shaft 166. Firstprobe body 160 includes a first end 172, a second end 174, and a firstprobe body tip 176 on second end 174. Second probe body 162 includes afirst end 178, a second end 180, and a second probe body tip 182 onsecond end 180. Second probe body 162 is coupled, using any suitableattachment, with shaft 166 at a first end 184 of shaft 166. Shaft 166extends generally perpendicularly from second probe body 162 andincludes a plurality of roller bearings 186 that are slidably coupled toshaft 166 and fixedly coupled to inspection tool assembly body 102.Shaft 166 is slidable within roller bearings 186 such that shaft 166 istranslatable and selectively positionable along axis 170 and withinroller bearings 186. Shaft 166 is coupled, using any suitableattachment, to connecting member 164 at a second end 188 of shaft 166.

[0031] Connecting member 164 extends from shaft second end 188 to firstprobe body 160 and is generally perpendicular to shaft 166. Connectingmember 164 includes an opening 190 extending through a length 192 ofconnecting member 164. In the exemplary embodiment, opening 190 andfirst probe body 160 are cylindrically shaped. A portion of first probebody 160 is received within opening 190 and fixedly secured withinopening 190, using any suitable means, for example threaded bolts andthreaded nuts. In an alternative embodiment, probe body 160 is moveablewithin opening 190 such that probe body 160 is translatable andselectively positionable along axis 168 within opening 190. Probe tip176 is moveable along axis 168 and within probe body 160. Morespecifically, probe tip 176 is translatable and selectively positionablealong axis 168 within probe body 160. Although snubber and racetrackprobe 108 is coupled to inspection tool assembly 100, first probe body160 and connecting member 164 are translatable and selectivelypositionable along axis 168, and, in addition, shaft 166, connectingmember 164, and second probe body 162 are translatable and selectivelypositionable along axis 170. Accordingly, first probe body 160,connecting member 164, shaft 166, and second probe body 162 are togethertranslatable and selectively positionable with respect to inspectiontool assembly body 102, and along both axes 168 and 170. Therefore,first probe body tip 176 and second probe body tip 182 are selectivelypositionable with respect to inspection tool assembly body 102 and eachother.

[0032] Movement of first probe body 160 along axis 168 is driven by anysuitable mechanism or means, including, but not limited to, a pneumaticsystem (not shown) coupled with first probe body 160, or a biasingmechanism. Furthermore, movement of first probe body tip 176 along axis168 is driven by any suitable mechanism or means, including, but notlimited to, a pneumatic system (not shown) coupled with first probe bodytip 176, or a biasing mechanism. In addition, movement of connectingmember 164, shaft 166, and second probe body 162 along axis 168 and axis170 is driven by any suitable mechanism or means. For example, in oneembodiment, movement of connecting member 164, shaft 166, and secondprobe body 162 along axis 168 and axis 170 is driven by a pneumaticsystem (not shown) coupled to at least one of connecting member 164,shaft 166, and second probe body 162. Alternatively, in anotherembodiment, movement of connecting member 164, shaft 166, and secondprobe body 162 along axis 168 and axis 170 is driven by a biasingmechanism.

[0033] When shroud segment 40 is in position with respect to inspectiontool assembly 100 to facilitate inspection of at least one of snubberthickness 90 and racetrack thickness 92, second probe body tip 182 ispositioned within either racetrack section passageway 54 or snubbersection passageway 68, and first probe body 160 is positioned along axis168 in a position with respect to shroud segment 40 facilitating contactbetween first probe body tip 176 and shroud segment 40. First probe bodytip 176 is then moved toward shroud segment 40, along axis 168, and withrespect to first probe body 160, until first probe body tip 176 contactseither groove bottom 82 or snubber section projection surface 88. Oncefirst probe body tip 176 contacts either groove bottom 82 or snubbersection projection surface 88, first probe body tip 176 remains incontact with either groove bottom 82 or snubber section projectionsurface 88 and remains fixed in position with respect to segment 40,fixture 101, and inspection tool assembly 100 during inspection ofeither snubber thickness 90 or racetrack thickness 92. First probe body160, however, continues to move with respect to first probe body tip176. Accordingly, first probe body 160 then moves along axis 168 awayfrom first probe body tip 176 and shroud segment 40 such that connectingmember 164, shaft 166, and second probe body 162 move along axes 168 and170 away from fixture 101 until second probe body tip 182 contactseither first passageway outer wall 62 or second passageway outer wall74. To determine snubber thickness 90, snubber and racetrack probe 108measures the location of first probe body tip 176 when probe tip 176 isin contact with projection surface 88, and measures the location ofsecond probe body tip 182 when probe tip 182 is in contact with outerwall 74. Snubber and racetrack probe 108 then compares the location ofprobe tip 176, with the location of probe tip 182, to determine snubberthickness 90. To determine racetrack thickness 92, snubber and racetrackprobe 108 measures the location of first probe body tip 176 when probetip 176 is in contact with groove bottom 82, and measures the locationof second probe body tip 182 when probe tip 182 is in contact with firstpassageway outer wall 62. Snubber and racetrack probe 108 then comparesthe location of probe tip 176 with the location of probe tip 182 todetermine racetrack thickness 92.

[0034] In operation, any of snubber thickness 90, racetrack thickness92, first shroud segment thickness 94, second shroud segment thickness96, first shroud segment length 98, or the second shroud segment lengthhave been machined by the machining apparatus, inspection tool assembly100 is orientated into a position with respect to fixture 101 and themachining apparatus to facilitate inspection of at least one of fixture101, snubber thickness 90, racetrack thickness 92, first shroud segmentthickness 94, second shroud segment thickness 96, first shroud segmentlength 98, and the second shroud segment length. Once positioned,inspection tool assembly 100 inspects at least one of fixture 101,snubber thickness 90, racetrack thickness 92, first shroud segmentthickness 94, second shroud segment thickness 96, first shroud segmentlength 98, and the second shroud segment length using the appropriateprobe 104, 106, 108, and/or 110. Inspection tool assembly 100facilitates accurately, quickly, and repeatably measuring criticaldimensions for a component, such as shroud segment 40. In oneembodiment, each measurement, including orientating segment 40 forinspection and measuring, takes approximately 30 seconds. Furthermore,and in another embodiment, each measurement can be repeated byinspection tool assembly 100 within an accuracy of 0.0002 inches. In yetanother embodiment, inspection tool assembly 100 inspects shroud segment40 with an accuracy substantially similar to the accuracy of a CMMmachine.

[0035] The above-described inspection tool is cost-effective, highlyreliable, and highly accurate for inspecting a component. The toolfacilitates accurate measurement of a thickness of the component withthe use of only one probe. In addition, the tool permits a component,such as a gas turbine engine shroud segment, to be accurately inspectedwithout removal from a machining apparatus. More specifically, becausethe inspection tool is coupled to at least one of a machining fixtureand a machining apparatus, the machining apparatus can automaticallyperform orientation of the tool. Therefore, the tool requires minimalinput from an operator and the cycle time is greatly reduced.Furthermore, the tool does not require extra floor space in amanufacturing area. As a result, the tool facilitates reducinginspection costs in a cost-effective and reliable manner.

[0036] Exemplary embodiments of tool assemblies are described above indetail. The systems are not limited to the specific embodimentsdescribed herein, but rather, components of each assembly may beutilized independently and separately from other components describedherein. Each tool assembly component can also be used in combinationwith other tool assembly components.

[0037] While the invention has been described in terms of variousspecific embodiments, those skilled in the art will recognize that theinvention can be practiced with modification within the spirit and scopeof the claims.

What is claimed is:
 1. A method for inspecting a component, said method comprising: coupling the component to a fixture such that the component is fixedly secured in position during machining of the component; and inspecting the component using an inspection tool while the component is coupled to the fixture.
 2. A method in accordance with claim 1 wherein coupling the component to a fixture further comprises machining the component using a machining apparatus while the component is coupled to the fixture.
 3. A method in accordance with claim 2 wherein inspecting the component further comprises coupling the inspection tool to at least one of the fixture and the machining apparatus.
 4. A method in accordance with claim 1 wherein inspecting the component further comprises measuring at least one of a thickness and a length of the component.
 5. A method in accordance with claim 1 wherein the inspection tool includes a probe having at least a first and a second probe tip, inspecting the component further comprises measuring a thickness of the component using the first and the second probe tips.
 6. A method in accordance with claim 5 wherein measuring a thickness of the component comprises: positioning the first probe tip in contact with a first surface of the component; positioning the second probe tip in contact with a second surface of the component; and determining a thickness of the component using the location of the first probe tip and the location of the second probe tip.
 7. An inspection tool comprising a first probe having a probe body, a first probe tip coupled to said probe body, and a second probe tip coupled to said probe body, said first probe configured to inspect a component using said first and second probe tips.
 8. An inspection tool in accordance with claim 7 wherein said first probe configured to measure a thickness of the component using said first and second probe tips.
 9. An inspection tool in accordance with claim 7 further comprising: a shaft including at least one roller bearing slidably coupled to said shaft; and a connecting member, said shaft coupled to said second probe tip and said connecting member, said first probe tip and said second probe tip selectively positionable with respect to each other.
 10. An inspection tool in accordance with 7 further comprising a second probe configured to measure a length of the component.
 11. An inspection tool in accordance with claim 7 further comprising a second probe configured to measure a location of a surface of a fixture used to fixedly secure the component in position during at least one of inspection and machining of the component.
 12. An inspection tool in accordance with claim 7 wherein the component is a gas turbine engine shroud segment including a snubber section, said first probe tip configured to contact a first surface of the snubber section, said second probe tip configured to contact a second surface of the snubber section, said probe configured to determine a thickness of the snubber section using the locations of said first and second probe tips.
 13. An inspection tool in accordance with claim 7 wherein the component is a gas turbine engine shroud segment including a racetrack section, said first probe tip configured to contact a first surface of the racetrack section, said second probe tip configured to contact a second surface of the racetrack section, said probe configured to determine a thickness of the racetrack section using the locations of said first and second probe tips.
 14. An inspection tool in accordance with claim 7 wherein said inspection tool coupled to a fixture, the fixture configured to couple with the component such that the component is fixedly secured in position with respect to the fixture during machining of the component, said inspection tool configured to inspect the component while the component is coupled with the fixture.
 15. An inspection tool in accordance with claim 7 wherein said inspection tool coupled to a machining apparatus used for machining the component, the machining apparatus comprises a fixture coupled thereto, the fixture configured to couple with the component such that the component is fixedly secured in position with respect to the fixture during machining of the component, said inspection tool configured to inspect the component while the component is coupled with the fixture.
 16. An inspection apparatus for inspecting a component, said inspection apparatus comprising: a machining apparatus configured to machine the component; a fixture coupled to said machining apparatus and configured to couple to the component such that the component is fixedly secured in position during machining of the component; and an inspection tool coupled to at least one of said fixture and said machining apparatus, said inspection tool configured to inspect the component while the component is coupled to said fixture.
 17. An inspection apparatus in accordance with claim 16 wherein said inspection tool comprising a probe coupled thereto and configured to measure a length of the component.
 18. An inspection apparatus in accordance with claim 16 wherein said inspection tool comprising a probe coupled thereto and configured to measure the location of a surface of said fixture.
 19. An inspection apparatus in accordance with claim 16 wherein said inspection tool comprising a probe coupled thereto and configured to measure a thickness of the component.
 20. An inspection apparatus in accordance with claim 19 wherein said probe comprising a probe body, a first probe tip coupled to said probe body, and a second probe tip coupled to said probe body, said probe configured to measure a thickness of the component using said first and second probe tip. 